Two stage gas turbine propulsion jet unit with thrust diverting means



June 14, 1966 H. J. GRIEB TWO STAGE GAS TURBINE PROPULSION JET UNIT WITHTHRUST DIVERTING MEANS 2 Sheets-Sheet 1 Filed Aug. 12, 1963 INVENTOR-HUBERT J. GRIEB A TTORNEYS June 14, 1966 H. J. GRIEB TWO STAGE GASTURBINE PROPULSION JET UNIT WITH THRUST DIVERTING MEANS 2 Sheets-Sheet 2Filed Aug. 12, 1963 INVENTOR.

HUBERT J. GRIEB QOQWMQ QM ATTORNEYS United States Patent "ice TWO STAGEGAS TURBINE PRGPULSION JET UNIT WITH THRUST DIVERTING MEANS Hubert J.Grieb, Stuttgart-Botnang, Germany, assignor to Daimler-BenzAktiengesellschaft, Stuttgart-Unterturkheim, Germany Filed Aug. 12,1963, Ser. No. 301,452

Claims priority, application Germany, Aug. 18, 1962,

23 Claims. (Cl. 60-3554) The present invention relates to a two-stagegas turbine jet propulsion unit for propelling vertical take-off andshort take-off airplanes, of which the first stage consists of one orseveral air compressors, one or several combustion chambers, one orseveral compressor drive turbines, and a channel bifurcation controlledby flaps or the like members which continues in a horizontal thrustchannel extending in the direction of the longitudinal axis of thepropulsion unit, and in a lift channel bent perpendicularly orapproximately perpendicularly to the longitudinal axis of the turbinepropulsion unit, within which rotate the turbine blades of liftcompressor rotors which draw in atmosphere for the second stage and alsosupply it to the aforementioned lift channel.

Two-stage jet propulsion units for vertical take-off planes are known inthe art,of which the gas generators together with the horizontal thrustchannel are arranged, for example, below the airfoil wing, while a liftcompressor rotor is built-in horizontally into the fuselage orpreferably within the airplane wing, which lift compressor rotorcomprises turbine blades radially outwardly thereof and compressorblades radially inwardly thereof. The turbine blades of the liftcompressor rotor are supplied with propulsion gases from the gasgenerator of the first propulsion unit stage by Way of a channelbranched off from the horizontal thrust channel and by an annularchannel extending around the compressor rotor. channel-bifurcation isthereby controlled by a flap which renders it possible to guide thepropulsion gases either only through the horizontal thrust channel oronly to the turbine blade ring of the lift compressor rotor or-- withintermediate positions of the control flap-to cause the propulsion gasesto flow both into the horizontal thrust channel as well as also to thelift compressor rotor so that lift and thrust components are generatedfor intermediate or transitional flights.

The disadvantages and drawbacks of these known propulsion units resideprimarily in that the airplane wing is structurally impaired by theinstallation of the largesurfaced lift compressor rotor, which will leadto complications particularly with the relatively thin wings of modernhigh-speed aircrafts. A further disadvantage consists in that theoutwardly provided turbine can only be loaded partially, which affectsadversely the turbine efficiency. Moreover, the necessity of a short andas straight as possible a connection between the lift unit and thethrust unit of the propulsion system Will unfavorably influence, undercertain conditions, the overall concept of an airplane.

Also known in the prior art for the installation in vertical take-offairplanes are gas turbine jet propulsion units with a two-stage forwardcompressor wherein one of the compressor stages supplies compressed airto the gas generator whereas the air compressed in thesecond compressorstage flows into a thrust channel with two pivotal thrust nozzlesarranged laterally forwardly on the propulsion unit and directedobliquely downwardly, for the vertical and the transitional as well asthe horizontal flight. Also the hot propulsion gases leaving thecompressor drive turbines are guided into a thrust channel The with twopivotally positioned thrust nozzles, provided laterally rearwardly onthe propulsion unit, for the horizontal and vertical flight.

A disadvantage of this latter propulsion unit arrangement consists inthat the forward diameter thereof becomes rather' large due to thetwo-stage forwardly disposed compressor and the pivotable thrustnozzles. A further important drawback consists in that even insupersonic airplanes, 'a considerably higher thrust is needed forstarting than for the horizontal flight so that the propulsion unit hasto be throttled in the latter flying condition. It is, therefore,impossible to provide with this type of prior art propulsion unit anarrangement which is equally favorable and optimal for the start ortake-off as well as for the normal flight. Additionally, only relativelysmall bypass conditions 'are structurally possible in this type ofpropulsion unit. For the start or take-off, however, the bypasscondition should be as high as possible with regard to the fuelconsumption and jet velocity, bearing a definite relation to grounderosion and noise, while relatively low bypass conditions are favorableduring the normal flight. Although the consumption rates of two-stagegas turbine propulsion units are more favorable .than those of onestagepropulsion units, with the use of lift-thrust propulsion units of knownconstruction the'consumption during horizontal flight will be largerthan that of one-stage propulsion units With the same thrust, since thetwo-stage propulsion unit has to be throttled. Another disadvantageresides in the fact that the large required air inlet, on the one hand,and the'pivotable nozzles which remain also in operation during thehorizontal flight, onthe other hand, entail a shape of the'airp'lanefuselage which is aerodynamically by no means optimal.

The present invention aims at the elimination of the aforementioneddisadvantages and drawbacks. In contrast to the propulsion units andsystems known in the prior art, the two-stage jet propulsion unit inaccordance with the present invention is characterized by the fact thatthe section of the lift channel sysem positioned ahead of the curved orelbow portions, as viewed in the direction of the lift flow, consists ofa turbine channel section coaxially disposed around theconcentrically-extending,

or rotors extending perpendicularly to the longitudinal axis of thepropulsion unit, carry radially outwardly thereof the air compressorblade ring, radially centrally thereof the turbine blade ring, andradially inwardly thereof a set of spokes rotating within the horizontalthrust channel and aerodynamically ineffectual.

A further feature of the present invention resides in that the liftchannel system consists of two branched channel sections which arebifurcated to the rear of the air inlet, and more particularly of aforward channel branch section initially directed forwardly andsubsequently bent downwardly, through which only air of the secondpropulsion unit stage is supplied, and of a rearward channel branchsection which is initially directed rearwardly and then bent downwardlyand which is supplied with propulsion gases of the first propulsion unitstage and with air of the second propulsion unit stage, which surroundsor jackets the hot propulsion gases.

Additionally, it is proposed in accordance with the present invention toprovide two lift compressor rotors of which one rotor is arranged withinthe forward channel Patented June 14, 1966 'cally connected in series.

branch section and the other rotor is arranged in the rearward channelbranch section.

In order to compensate for any gyroscopic moments of the lift compressorrotors, it is advantageous to cause in accordance with the presentinvention the two rotors to rotate in mutually opposite directions.

The air inlet or inflow into the second propulsion unit stage takesplace, according to the present invention, over the entire orapproximately over the entire circumference of the propulsion unit andis controlled by ad justable elements, such as flaps, or the like.

The following advantages are achieved by the present invention:

The propulsion unit as a whole is equally suitable for installation inthe airplane fuselage or in the nacelles. For this reason, a favorablearrangement is possible, for example, of an after-burner installationwithin the flow channel ahead of the horizontal thrust nozzles in thetail section of the fuselage. In contrast to the known two-stagepropulsion units having a forwardly disposed two-stage compressor inwhich the pivotable lift-thrust nozzles are loaded constantly andtherefore have to be spaced from the Walls of the plane fuselage arelatively large distance, the pivotable thrust nozzles of the liftinstallation in accordance with the present invention are in operationonly during vertical flights and transitional flying conditions so thatthey may be installed more favorably in the walls of the fuselage. Theradially outwardly disposed lift compressor blades and theradiallyinwardly disposed turbine blades permit of any desired largebypass condition, that is, compressor flow rate/propulsion unit flowrate, which will result in a ratio between horizontal thrust andvertical thrust that may be varied within relatively wide limits so thata favorable adaptation is possible for airplanes with different speedranges.

With an arrangement or two rotors, one for a forward lift branch channelsection and one for a rearward lift branch channel section, the turbinesare flow-dynami- The turbine head is thereby subdivided which has afavorable effect on the aerodynamic load of the turbines. For thatreason, relatively high bypass conditions may still be realized in aonestage arrangement of the turbines with a still relatively high degreeof efliciency. Only with extremely large bypass conditions is itadvisable to equip the compressor rotors with two turbine stages. Thiswill not require, however, any additional space since the distancebetween two compressor rotors, which has to be present in view of theinflow of the air of the second stage, need not be increased.

For all of the foregoing reasons, particularly in view of the largebypass condition, there will result a specific, low fuel consumption forstart and landing, extremely low jet stream velocities during take-offand landing to avoid ground erosions and noise, and a low compressionratio of the lift compressors and therewith a high flexibility in theoperating behavior. Moreover, each of the two air inlets for thehorizontal thrust part and the lift part of the overall installation maybe arranged and constructed in an optimum manner according to itsfunction, whereby the relatively small air inlet for the horizontalthrust part may be readily accommodated in the structure of the airplanefuselage, while the relatively large air inlet of the lift installation,distributed over the entire circumference of the fuselage, does notrequire any additional fuselage cross section. the lift unit is closedduring the horizontal flight so that it cannot exert any negativeinfluence on the aerodynamics of the airplane. Calculations have shownthat with two lift compressor rotors, the required cross section for thefuselage or nacelle is considerably smaller, even in Case of anextremely high bypass condition, than with comparable known lift-thrustpropulsion units. Even with a single compressor rotor, the requiredcross The air inlet of 1 section of the fuselage or nacelle is largeronly in case of extremely high bypass conditions than that necessitatedfor the known lift-thrust propulsion units which do not attain suchextremely high bypass conditions.

Furthermore, the outer cold air jet of the second propulsion unit stageforms in the rearward lift channel branch section a heat-insulatingjacket about the inner, hot propulsion gas jet of the first propulsionunit stage.

Accordingly, it is an object of the present invention to provide atwo-stage gas-turbine propulsion unit of the type described hereinabovewhich effectively avoids the drawbacks and shortcomings encountered withthe prior art constructions yet enables a relatively simple installationfrom constructional points of view that do not require additionalexpenditures over and above those of the prior art constructions.

Another object of the present invention resides in the provision ofgas-turbine propulsion units for airplanes, particularly verticaltake-off and short take-off aircrafts which are so constructed as not toimpair the aerodynamic design of the craft, especially which are soconstructed as not to lead to complications in the supersonic wingstructures of presently known aircraftdesigns.

Still another object of the present invention resides in the provisionof a two-stage gas-turbine propulsion unit which assures a high degreeof efficiency of the turbine operation under all flight conditions, thatis, during vertical take-off and landing as well as during normalflights.

A further object of the present invention resides in the provision of agas turbine propulsion unit for aircrafts which permits optimumutilization of the propulsion units for vertical take-off and horizontalflight conditions, even with supersonic speeds and which enablesrelatively large bypass conditions without excessive encumberances ofthe construction.

Still another object of the present invention resides in the provisionof a gas-turbine propulsion unit for vertical take-off planes thatoffers relatively low fuel consumption under all operating conditions,permits of relatively small dimensions of the propulsion installationand of the airplane parts enclosing the same, and which also permits anoptimum design of the airplane fuselage notwithstanding the existence ofadjustable inlet apertures provided therein.

A further object of the present invention resides in the provision of agas-turbine propulsion unit for vertical take-off planes that may bereadily installed within a given airplane fuselage, permits the use ofan afterburner installation and which enables the choice, withinrelatively wide limits, of suitable ratios between the hori zontal andvertical thrusts for good adaptation to planes with different velocityranges.

Another object of the present invention resides in the provision ofgas-turbine propulsion units for a vertical take-off plane in which thepressure heads of the turbines are effectively subdivided therebyproviding good aerodynamic loading of the turbines.

Still a further object of the present invention resides in the provisionof a gas-turbine propulsion unit for vertical take-off planes whichassures relatively low jet velocities during take-off and landingnotwithstanding a relatively low specific fuel consumption during thetake-off and starting operations coupled with relatively large bypassconditions and high flexibility in the operation thereof.

Another object of the present invention resides in the provision of agas-turbine propulsion unit for vertical take-off planes in which theinstallations producing the horizontal and vertical thrusts may each beconstructed in an optimum manner without the danger of mutualinterference resulting in an adverse influence on the aerodynamics ofthe airplane.

Still another object of the present invention resides in the provisionof a gas-turbine propulsion unit of the type described hereinabove inwhich the lift unit is so constructed and arranged as to provide arelatively effective heat-insulating jacket consisting of cool air forthe hot propulsion gases derived from the gas generator.

These and other objects, features, and advantages of the presentinvention will become more obvious from the following description, whentaken in connection with the accompanying drawing, which shows, forpurposes of illustration only, two embodiments in accordance with thepresent invention, and wherein FIGURE 1 is a longitudinalcross-sectional view through a two-stagepropulsion unit with two thrustcompressor rotors in accordance with the present invention;

FIGURE 2a is a cross-sectional view, taken along line 11-11 of FIGURE 1with the air inlet (flaps of the compressor thrust stage in the closedposition thereof;

FIGURE 2b is a cross-sectional view, also taken along line II]1 ofFIGURE 1, with the air inlet flaps of the compressor thrust stage in theopen position thereof;

FIGURE 3 is a cross-sectional view taken along line III-HI of FIGURE 1,and

FIGURE 4 is a longitudinal cross-sectional view through a modifiedtwo-stage propulsion unit having a single thrust compressor rotor inaccordance with the present invention.

Referring now to the drawing wherein like reference numerals are usedthroughout the various views to designate like parts, the first stage ofthe propulsion units of FIGURES l and 4 consists essentially of an aircompressor -11, of a plurality of combustion chambers 12; of acompressor drive turbine 13, and of a channel bifurcation generallydesignated by reference numeral 14 which is adjoined, on the one hand,by horizontal thrust channel 15, provided with a horizontal thrustnozzle 16 having an adjustable cross section. The entire lift channelsystem according to FIGURE 1 consists of a forward branch lift channelsection generally designated by reference character K and of a rearbranch lift channel section generally designated by reference characterK The lift channel system according to FIGURE 4 has only a rear channelbranch section generally designated by reference character K The channelbifurcation 14, which is controlled by a flap 21 is adjoined, on theother hand, by a turbine channel section K which is surrounded orjacketed by an air channel section K and K respectively, at the ends ofwhich are provided pivotable thrust nozzles 18 and 19. The channelsections K K and K thus extend coaxially about the forward part of thehorizontal thrust channel 15. An after-burner installation 20 may beprovided in the rearward part of the horizontal thrust channel 15. Y

Two lift compressor rotors a and b (FIG. 1) are freely rotatablysupported in the engine housing of the propulsion unit of FIGURE 1. InFIGURE 4, only a single such lift compressor rotor c is freely rotatablysupported in the engine housing thereof. The rotors a and b or c carryturbine blades .22 which rotate within the propulsion gas channelsection K and air compresor blades 23 which rotate Within the airchannel sections K and K respectively. Moreover, the rotors a and b or care provided with aerodynamically ineffectual spokes 24 which rotatewithin the thrust channel 15.

The air inlet generally designated by reference numeral 25 of the secondpropulsion unit stage, i.e., of the lift compressor stage, is controlledby pivotable flaps 26 and air scoops 27, adapted to be extended andretracted, Within the lower part of the circumference of the propulsionunit. Instead of air inlet flaps 26 and airinlet scoops 27, a tubularslide member 30 is provided in FIGURE 4. =Iniflatable edges or bulges-29 improve, during suspended and intermediate flights, the aerodynamicconditions of the propulsion unit and of the airplane.

-It is, of course, well possible Within the scope of the presentvinvention to arrange within the thrust channel 17 fuel injection devices28 for increasing the thrust.

6 OPERATION The operation of the illustrated propulsion units is asfollows:

During suspended and intermediate flights, the control flaps '21 are inthe position thereof shown in dash lines, i.e., the horizontal fiightchannel 15 is blocked. The propulsion gases T leaving the compressordrive turbine 13 flow into the lift channel system, thereby loading oracting on the turbine blades 22, rotating within the channel section Kof rotors a and b or c, and then flow through the bent or elbow portionK whereupon they leave the propulsion unit through the pivotable thrustnozzles 19. The air inlet flaps 26 and scoops 27 or the slide member 30,respectively, are in the open position in the aforementioned flightconditions so that atmospheric air A may flow in, which is drawn in,compressed, and supplied to the elbow portion K by the compressor blades23. The propulsion gas jet leaving the two thrust nozzles 19 is thuscomposed of an inner hot tubular jet stream consisting of turbine gasesT and of an outer jacketing stream consisting of compressed,considerably colder air A. Only relatively cold air A is supplied by thecompressor rotor a through the lift branch channel section K (FIG. 1),which is discharged through the two forward thrust nozzles 18. Thethrust nozzles 18 and 10 are so constructed and adjustable arranged in amanner, known per se, that the propulsion gases T or A and T,respectively, are able to flow out in the form of from vertically tohorizontally directed jets.

During the horizontal flight, the control :flap 21 assumes the positionillustrated in the drawing in full lines; the air inlet elements 26 and27 or 30, respectively, thereby close the fuselage about the nacelle andtherewith seal the compressor thrust stage against the outside. Thepropulsion gases T will then flow exclusively through the horizontalthrust channel 15 without driving the lift compressor rotors a and b or0 since the spokes 24 thereof are aerodynamioally ineffective.

While I have shown and described herein two embodiments in accordancewth the present invention, it is understood that the same is not limitedthereto, but is susceptible of many changes and modifications within thespirit and scope of the present invention; and I, therefore, do not wishto be limited to the details shown and described herein, but intend tocover all such changes and modifications as are encompassed by the scopeof the appended claims.

I claim:

1. A two-stage gas turbine jet propulsion unit, for propelling verticaltake-01f and short take-off aircrafts, comprising:

a first propulsion unit stage including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith the output of said turbine means and continuing, on the one hand,in horizontal thrust channel means forming part of said first stage and,on the other, in lift channel means having a first section operativelyconnected with said channel branching means and surrounding saidhorizontal thrust channel means substantially coaxially, a secondsection surrounding said first section and elbow section meansoperatively connected with said first and second sections and bentapproximately at right angle to said longitudinal axis, and controlmeans in said channel branching means and operable to selectivelycontrol the opening and closing of said thrust and lift channel means;

a second propulsion unit stage including said lift channel means andlift compressor rotor means operable to draw in outside air for saidsecond stage and supply the same to said lift channel means, and saidsecend section forming an air channel section provided with air inletmeans disposed along the circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means disposed in said second section, radiallycentrally thereof turbine blade means disposed within said first sectionand radially inwardly thereof a set of spokes that are iaerodynamicallyineffectual and rotate within said horizontal thrust channel means.

thrust and lift channel means,

a second propulsion unit stage including said lift channel means andlift compressor rotor means operable to draw in outside air for saidsecond stage and sup- 2. A two-stage gas turbine jet propulsion unit,for pro- 10 pelling vertical take-off and short take-0E aircrafts,comprising:

a first propulsion unit stage including air compressor means, combustionchamber means operatively conoutwardly thereof air compressor blademeans disposed in said second section, radially centrally thereofturbine blade means disposed within said first secply the same to saidlift channel means and said nected with said air compressor means, andicomsecond section forming an air channel section propressor-driveturbine means operatively connected vided with air inlet means disposedalong the circumwith said combustion chamber means, ference of thepropulsion unit, channel system including channel branching means andsaid lift compressor rotor means carrying radially operatively connectedwith output of said turbine outwardly thereof air compressor blade meansdismeans and continuing, on the one hand, in horizontal posed in saidsecond section, radially centrally therethrust channel means formingpart of said first stage of turbine blade means disposed within saidfirst and, on the other, in lift channel means having a first sectionand radially inwardly thereof a set of spokes section operativelyconnected with said channel that are aerodynamically ineffectual androtate withbranching means and surrounding said horizontal in saidhorizontal thrust channel means, thrust channel means substantiallycoaxially, a secsaid lift channel means being effectively provided withond section surrounding said first section and elbow two channel branchsections which branch off to the section means operatively connectedwith said first rear of said air inlet means, as viewed in the directionand second sections and bent approximately at right of flow of theoutside air, one of said branch sections angle to said longitudinalaxis, and control means being a forward, initially forwardly directedand in said channel branching means and operable to subsequentlydownwardly bent lift-channel branch selectively control the opening andclosing of said section forming one of said elbow section means thrustand lift channel means; through which is supplied the air of the seconda second propulsion unit stage including said lift chanpropulsion unitstage, and the other branch section nel means and lift compressor rotormeans operable b ing a rear, initially rearwardly directed and subsetodraw in outside air for said second stage and quently downwardly bentlift-channel branch section supply the same to said lift channel means,and said forming the other of said elbow section means which secondsection forming an air channel section prois supplied with propulsiongases of the first propulvided with air inlet means disposed along thecircumsion unit stage and with air of the second propulsion ference ofthe propulsion unit, unit stage jacketing the hot propulsion gases, andsaid lift compressor rotor means carrying radially Said lift compressorrotor means including two rotors,

one of said last-mentioned rotors being arranged within the forwardlift-channel branch section and the other in the rear lift-channelbranch section.

4 A two stage gas turbine jet propulsion unit, for propelling verticaltake-off and short take-off raircrafts, comprising:

a first propulsion unit stage including air compressor tion and radiallyinwardly thereof a set of spokes that are aerodynamically ineffectualand rotate within said horizontal thrust channel means,

said lift channel means being effectively provided with two channelbranch sections which branch off to the rear of said air inlet means, asviewedin the direcrneans, combustion chamber means operatively connectedwith said air compressor means, and comprestion of fiow of the outsideair, one of said branch sor-drive turbine means operatively connectedwith sections being a forward, initially forwardly directed Saidcombustion chamber means,

and subsequently downwardly bent lift-channel channel system includingchannel branching means branch section forming one of said elbow sectionp r iv ywith iihcoll'tpllt'of Said tflllfbifie means through which issupplied the air of the secmeans and continuing, on the one hand, inhorizontal ond propulsion unit stage, and the other branch secchannelmeans forming P Of Said first Stage tion being a rear, initiallyrearwardly directed and and, on the other, in lift channel means havinga first subsequently downwardly bent lift-channel branch sectionoperatively connected with said channel section forming the other ofsaid elbow section means branching mflans and Surrounding Saidhorizontal which is supplied with propulsion gases of the first thrustchannel means substantially coaxially, a second propulsion unit stageand with air of the second Section surrounding said first section andelbow secpropulsion unit stage jacketing the hot propulsion gases.

tion means operatively connected with said first and second sections andbent approximately at right angle to said longitudinal axis, and controlmeans in said channel branching means and operable to selectivelycontrol the opening and closing of said thrust and lift channel means,

a second propulsion unit stage including said lift chan- 3. A two-stagegas turbine jet propulsion unit, for propelling vertical take-off andshort take-off a'ircrafts, comprising:

a first propulsion unit stage including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with nel means andlift compressor rotor [means operable to draw in outside air for saidsecond stage and supply said combustion chamber means, the same to saidllift channel means, and said second channel system including channelbranching means section forming an :air channel section provided withoperatively connected with the output of said turbine air inlet meansdisposed along the circumference of means and continuing, on the onehand, in horizontal the propulsion unit,

thrust channel means forming part of said first stage and said liftcompressor rotor means carrying radially and, on the other, in liftchannel means having a first outwardly thereof air compressor blademeans dis- 9 posed in said second section, radially centrally thereofturbine blade means disposed Within said first section and radiallyinwardly thereof aset of spokes that are aerodynamically ineffectual androtate within within the forward lift-channel branch section and theother in the rear lift-channel branch section.

10 a channel system including channel branching means operativelyconnected with the output of said turbine means and continuing, on theone hand, in horizontal thrust channel means forming part of said firststage said horizontal-thrust channel means, and, onthe other,-in liftchannel means having a said lift channel means'beingeffeotively providedwith first section operatively-connected with said channel two channelbranch sections which branch off to the branching means and surroundingsaid horizontal rearof said air inlet means, as viewed in thedirecthrust with said channel branching channel means tion of flow ofthe outside air, one of said branch substantially'coaxially, a secondsection surrounding sections being a forward, initially forwardlydirected said first section and elbow section means operatively andsubsequently downwardly bent lift-channel connected with said first andsecond sections and bent branch section forming one of said elbowsection approximately at right angle to said longitudinal means throughwhich is supplied the air of the second axis, and control means in saidchannel branching propulsion unit stage, and the other branch sectionmeans'and operable to selectively control the open being a rear,initially rearwardly directed and subsemg and closing of said thrust andlift channel means, quently downwardly =ben-t lift-channel branchsection a second propulsion zunit stage including said lift chan formingthe other of said elbow section means which nel means and liftcompressor rotor means operable is supplied With propulsion gases of thefirst-propulto 'draw in outside air for said second stage and supsionunit stageiand with air of the second propulsion ply the-same; to saidlift channel means, and said secunit stage jacketing the hot propulsiongases, 1 d s c i n fi ming an air channel section provided said liftcompressor rotor means including two rotors, with air inlet meansdisposed along the circumference one of said last-mentioned rotors beingarranged of the propulsion unit, within the forward lift-channel branchsection and and said lift compressor rotor means carrying radially theother in the rear lift-channel branch section, outwardly thereof aircompressorblade means disthe direction of rotation of the twolast-mentioned roposed in said second section, radiallycentrally-theretors being in opposite directions. of turbinetblade meansdisposed within said first sec- 5. A two-stage gas turbine jetpropulsion unit, for prod ally inwafdly'theleof of Spokes that pelling;vertical takeeofi and short take otf aircrafts,comare:aemdynamically-iI1efieCtl1a1 and rotate Within prising; saidhorizontal thrust channel means,

a firstnpropulsion. unit stage including air compressor 3 Said liftcompressor rotor means including two rotors, means, combustion chambermeans operatively con- One ofsaid last-mentioned rotors being arrangednected with said air compressor 111 3115, and comwithin the forwardlift-channel branch section and pressor-drive turbine means operativelyconnected the-Other in I reE11 lift-Channel bfahchsecfioh, i h id b ti hb means, the direction of rotation-of the two last-mentioned a channelsystem including channel. branching means i rotors bfiihgoppositeldifectionsoperatively connected withtheoutput of said turbine Atwo-Stage gas turbine l P punit, P means d i i on 1116,0116 h d i h i tl pelling vertical take-off and short take-off aircrafts, comthrustchannel means forming part of said first stage Prlslng! and, on theother, in lift channel means having; a first a i P p i "unit Stageincluding air compressor section operatively connected with said channel40 means, Combustion c amber means operatively conbranching means andsurrounding said horizontal nected With- Said compressor means, andthrust channel means substantially coaxially, a secspfessof-dfiveiufbhle means operatively connected ond section surrounding said firstvsection and ,elbow With Said o b stion chamber means, section meansoperatively connected .with said first a fi System hlchldhlg channelbranching means and second sections and bent approximately at right pfia y cQhllectedkwith the p of Said turbine angle to said longitudinalaxis, and control means in means and-Continuing, 011 the one hand, illont l said channel branching means and operable to. selecthrustchannelemeans forming p of Said first stage tively control the openingand closing of said thrust n 011th? intlifi Channel means having a firstandlift channel means, section operatively connected with said channel asecond propulsion unit stage including said-lift chanbranching-meansSurrounding Said horizontal nel means and lift compressor rotor meansoperable thrust Channel means Substantially coaxially, a Second to drawin outside air for aid econd stageand supsection'surounding said firstsection andxelbow SCCtlOIl ply the same to said lift channel means, andsaid secmeaHS'OPEIatiVEIY connected with said first and second sectionforming an air channel section provided ondrsections and hem PP Y atright angle with air inlet means disposed along the circumference saidlongitudinal flXiS, and Control eans in Said of h Propulsion i channelbranching means and operable to selectively and said lift compressorrotor means carrying radially 6911301 the Opening and closing of saidthrust and outwardly thereof air compressoriblade means dishftchalmel11163115,

, posed in said second section, radially centrally therea Second P puunit Stage including Said lift Challof turbine blade means disposedwithin said first secnel means and lift compressor Iotol' means Operabletion and radially inwardly there-ofaset of spokes that to draw inOutside Said Second Stage and are aerodynamically inefiectual and rotatewithin said pp y the same to Said lift channel means, and Said h i lthrust h l means, 7 second section forming an air channel sectionprosaid lift compressor rotor means including two rotors, Vided With airinlet means i p along thfi one of said last-mentioned rotors beingarranged cumference ofthe Pmpulsioh unit,

and said lift compressor rotor means carrying radiallyoutwardly-=thereof air compressor 'blade means dis- 6. A two-stage gasturbine jet propulsionunit, for propelling vertical take-off and shorttake-01f aircrafts, comprising:

a first propulsion unit stage including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

posed in said second section, radially centrally thereof turbine blademeans disposed within said first section and radially inwardlythereof aset of spokes 3,255,584 1 1 l 2 8. A two-stage gas turbine jetpropulsion unit, for proa channel system including channel branchingmeans pelling vertical take-off and short take-off aircrafts,comoperatively connected with the output of sa1d turbine prising: meansand continuing, on the one hand, n horizontal a first propulsion unitstage including air compressor thrust channel means forming part of saidfirst cycle means, combustion chamber means operatively con- 5 and, onthe other, in lift channel means having a first nected with said aircompressor means, and comsection operatively connected with said channelpressor-drive turbine means operatively connected branching means andsurrounding said horizontal with said combustion chamber means, thrustchannel means, a second section surrounding channel system includingchannel branching means said first section and elbow section meansoperatively operatively connected with the output of said turbineconnected with at least one of said first and second means andcontinuing, on the one hand, in horizontal sections and bent at an angleto the longitudinal axis thrust channel means forming part of said firststage of the unit, and control means in said channel branchand extendingsubstantially in the longitudinal axis of ing means and operable toselectively control the the propulsion unit and, on the other, in liftchannel opening and closing of said thrust and lift channel means havinga first section operatively connected means,

with said channel branching means and surrounda second propulsion unitcycle including said lift chaning said horizontal thrust channel meanssubstannel means and lift compressor rotor means operable tiallycoaxially, a second section surrounding said to draw in atmospheric airfor said second cycle and first section and elbow section meansoperatively supply the same to said lift channel means, and airconnected with said first and second sections and inlet means incommunication with said second secbent approximately at right angle tosaid longitution and disposed along the circumference of the prodinalaxis, and control means in said channel branchpulsion unit,

ing means and operable to selectively control the and said liftcompressor rotor means carrying radially opening and closing of saidthrust and lift channel outwardly thereof air compressor blade meansdismeans, posed in said second section, radially inwardly thereof asecond propulsion unit stage including said lift channel means and liftcompressor rotor means operable to draw in outside air for said secondstage and supply the same to said lift channel means, said first a setof spokes that rotate within said horizontal thrust channel means, andradially intermediate therebetween turbine blade means disposed withinsaid first section.

and second sections being disposed ahead of the respective elbow sectionmeans, as viewed in the direction of the flow of the lift medium, andsaid second 10. A two-cycle gas turbine jet propulsion unit, comprising:

a first propulsion unit cycle including air compressor section formingan air channel section surrounding said turbine channel section andbeing provided with within the forward lift-channel branch section andthe other in the rear lift-channel branch section,

the direction of rotation of the two last-mentioned rotors being inopposite directions,

means, combustion chamber means operatively connected with said aircompressor means, and comair inlet means disposed along thecircumference of pressor-drive turbine means operatively connected thepropulsion unit, with said combustion chamber means,

and said lift compressor rotor means carrying radially channel systemincluding channel branching means outwardly thereof air compressor blademeans disoperatively connected with the output of said turbine posed insaid second section, radially centrally theremean and ontinuing, on theone hand, in horizontal of turbine blade means disposed within saidfirst 40 thrust channel means forming part of said first cycle Sectionand radially wardly thereof a set of spokes and, on the other, in liftchannel means having a first that are aerodynamically ineffectual androtate within section operatively connected with said channel saidhorizontal thrust channel means, branching means and surrounding saidhorizontal said lift channel means being effectively provided Withthrust channel means, a second section surrounding two channel branchsections which branch off to the said first section and elbow sectionmeans operatively rear of S id air inlet moans, as viewed in thedirecconnected with at least one of said first and second tion of flowof the outside air, one of said branch secsections and bent at an angleto the longitudinal axis ti being a forward, initially forwardlydirected of the unit, and control means in said channel branchandsubsequently downwardly b nt l t-Ch nn l ing means and operable toselectively control the branch section forming one of said elbow section5 opening d closing of id th t d lif h l means through which is suppliedthe air of the second means, Propulsion unit Stage, and the other branchSection a second propulsion unit cycle including said lift chanboing aroar, initially roarwal'dly directed and Sllbnel means and liftcompressor rotor means operable sequently downwardly bent lift-channel banch 80- to draw in atmospheric air for said second cycle and tionforming the other of said elbow section means supply th same t id lift hl means, d i which is supplied with propulsion gases of the first inletmeans in communication with said second secpropulsion unit stage andwith air of the second protion and disposed along the circumference ofthe pulsion unit stage jacketing the hot propulsion gases, propulsionunit,

said lift compressor rotor means including two rotors, and said liftcompressor rotor means carrying radially one of said last-mentionedrotors being arranged outwardly thereof air compressor blade meansdisposed in said second section, radially inwardly thereof a set ofspokes that rotate within said horizontal thrust channel means, andradially intermediate therebetween turbine blade means disposed withinsaid first section,

each of said lift compressor rotor means being 'provided with twoturbine stages formed by two turbine blade rings.

9. A two-cycle gas turbine jet propulsion unit, comprising:

a first propulsion unit cycle including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means, 75

the air inlet means of the second cycle effectively taking placeapproximately over the entire circumference of the propulsion unit, andadjustable control means for controlling said last-mentioned air inletmeans. 11. A two-stage gas turbine jet propulsion unit, for propellingvertical take-off and short take-01f aircrafts, comprising:

a first propulsion unit stage including air compressor means, combustionchamber means operatively connected with said air compressor means, andcom- 13 pressor-d-rive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith the output ofsaid turbine means and continuing, on the one hand, inhorizontal thrust channel means forming part of said first stage :andextending substantially in the longitudinal axis of the propulsion unitand, on the other, in lift channelmeans having a first sectionoperatively connected with said channel branching means and surroundingsaid horizontal thrust channel means, a second section surrounding saidfirst section and elbow section means operatively connected with saidfirst and second sections and bent approximately at right angle to saidlongitudinal axis, and control means in said channel branching means andoperable to selectively cont-r01 the opening and closing of said thrustand lift channel means,

a second propulsion unit stage including said lift channel means andlift compressor rotor means operable to draw in atmospheric air for saidsecond stage and supply the same to said lift channel means, and saidsecond section effectively constituting an air channel sectionsurrounding said first channel section and being provided with air inletmeans disposed along the circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means disposed in said second section, radiallycentrally thereof turbine blade means disposed within said first sectionand radially inwardly thereof a set of spokes that rotate within saidhorizontal thrust channel means, the air inlet means of the second stageeffectively taking place approximately over the entire circumference ofthe propulsion unit, and adjustable control means for controlling saidlast-mentioned air inlet means including extensible and retractable airscoop means provided within the lower region of the propulsion unitcircumference for the control of the air inlet means, and pivotal flapmeans arranged in the remaining portion of the propulsion unitcircumference. 12. A two-cycle gas turbine jet propulsion unit,comprising:

a first propulsion unit cycle including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith the output of said turbine means and continuing, on the one hand,in horizontal thrust channel means forming part of said first cycle and,on the other, in lift channel means having a first section operativelyconnected with said channel branching means and surrounding saidhorizontal thrust channel means, a second section surrounding said firstsection and elbow section means operatively connected with at least oneof said first and second sections and bent at an angle to thelongitudinal axis of the unit, and control means in said channelbranching means and operable to selectively control the opening andclosing of said thrust and lift channel means,

a second propulsion unit cycle including said lift channel means andlift compressor rotor means operable to drawin atmospheric air forsaidsecond cycle and supply the same to said lift channel means, and airinlet means in communication with said second section and disposed alongthe circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means disposed in said second section, radiallyinwardly thereof a set of spokes that rotate within said horizontalthrust channel means, and radially intermediate 1.4 therebetween turbineblade means disposed within said first section, fuel injection meansprovided within at least some of the air channel sections of the secondpropulsion unit cycle for additionally reinforcing the lift effect. 13.A two-stage gas turbine jet propulsion unit, for

propelling vertical take-off and short take-ofi aircrafts, comprising:

a first propulsion unit stage-including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith theoutput of said turbine means and continuing, on the one hand, inhorizontal thrust channel means forming part of said first stage andextending substantially in the longitudinal axis of the propulsion unitand, on the other, in lift channel means having a first sectionoperatively connected with said channel branching means and surroundingsaid horizontal thrust channel means, a second section surrounding saidfirst section and elbow section means operatively connected with saidfirst and second sections and bent approximately at right angle to saidlongitudinal axis, and control means in said channel branching means andoperable to selectively control the opening and closing of said thrustand lift channel means,

a second propulsion unit stage including said lift channel means andlift compressor rotor means operable to draw in atmospheric air for saidsecond stage and supply the same to said lift channel means, and saidsecond section effectively forming an air channel section surroundingsaid first channel section and provided with air inlet means disposedalong'the circumference of the propulsion unit, I

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means disposed in said second section, radiallycentrally thereof turbine blade means disposed within said first sectionand radially inwardly thereof a set of spokes that rotate within saidhorizontal thrust channel means,

the air inlet means of the second stage effectively taking placeapproximately over the entire circumference of the propulsion unit, andadjustable control means for controlling said last-mentioned air inletmeans including tubular slide means movable in theraxial direction forselectively controlling the air inlet means of said second stage.

14; A two-cycle gas turbine jet propulsion unit, comprising:

a first propulsion unit cycle including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith the output of said turbine means and continuing, on the one hand,in horizontal thrust channel means forming part of said first cycle,and, on the other, in lift channel meanshaving a first sectionoperatively connected with said channel branching means and surroundingsaid horizontal thrust channel means, a second section surrounding saidfirst section and elbow section means operatively connected with atleast one of said first and second sections and bent approximately at anangle to the longitudinal axis of the unit, and control means in saidchannel branching means and operable to selectively control the openingand closing of said thrust and lift channel means,

a second propulsion unit cycle including said lift channel means andlift compressor rotor means operable to draw in atmospheric air, forsaid second cycle and supply the same to said lift channel means, andair inlet means in communication with said second section and disposedalong the circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means disposed in said second section, radiallycentrally thereof turbine blade means disposed within said first sectionand radially inwardly thereof a set of spokes that rotate within said-horizontal thrust channel means,

and two lateral downwardly and outwardly directed pivotally arrangedthrust nozzle means provided at the end of each respective elbow sectionmeans.

15. A two-cycle gas turbine jet propulsion unit, comprising:

a first propulsion unit cycle including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith the output of said turbine means and continuing, on the one hand,in horizontal thrust channel means forming part of said first cycle and,on the other, in lift channel means having a first section operativelyconnected with said channel branching means and surrounding saidhorizontal thrust channel means, a second section surrounding said firstsection and elbow section means operatively connected with at least oneof said first and second sections and bent at an angle to thelongitudinal axis of the unit, and control means in said channelbranching means and operable to selectively control the opening andclosing of said thrust and lift channel means,

a second propulsion unit cycle including said lift channel means andlift compressor rotor means operable to draw in atmospheric air for saidsecond cycle and supply the same to said lift channel means, and airinlet means in communication with said second section and disposed alongthe circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means disposed in said second section, radiallyinwardly thereof a set of spokes that rotate within said horizontalthrust channel means, and radially intermediate therebetween turbineblade means disposed within said first section,

and after-burner means in the horizontal thrust channel means of thefirst propulsion unit stage.

16. In a two-stage gas turbine jet propulsion unit, for propellingvertical take-01f and short take-off aircrafts, which includes a firstpropulsion unit cycle with air compressor means, combustion chambermeans and compressor-drive turbine means; a channel system including achannel bifurcation operatively connected with the output of saidturbine means and continuing, on the one hand, in a horizontal thrustchannel and extending substantially in the longitudinal axis of thepropulsion unit and, on the other, in lift channel bent at an angle tosaid longitudinal axis, and control means in said bifurcation operableto selectively control the opening and closing of said thrust and liftchannels; and a second propulsion unit cycle including lift compressorrotor means oper' able to draw in atmospheric air for said second cycleand supply the same to said lift channel, andair inlet means for thesecond cycle disposed along the circumference of the propulsion unit,

the improvement essentially consisting of blade means carried by saidlift compressor rotor means including air compressor blade meansdisposed radially outwardly thereof, a set of spokes radially inwardlythereof that are aerodynamically substantially ineffectual and rotatewithin said thrust channel means, and turbine blade means intermediatesaid air compressor blade means and said spokes.

said lift channel including an initially approximately longitudinallydirected and subsequently downwardly bent lift-channel branch which issupplied with propulsion gases of the first propulsion unit cycle andwith air of the second propulsion unit cycle.

17. A two-cycle gas turbine jet propulsion unit, comprising:

a first propulsion unit cycle including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith the output of said turbine means and continuing, on the one hand,in horizontal thrust channel means forming part of said first cycle and,on the other, in lift channel means having a first section operativelyconnected with said channel branching means and surrounding saidhorizontal thrust channel means, a second section surrounding said firstsection and elbow section means operatively connected with at least oneof said first and second sections and bent at an angle to thelongitudinal axis of the unit, and control means in said channelbranching means and operable to selectively control the opening andclosing of said thrust and lift channel means,

a second propulsion unit cycle including said lift channel means andlift compressor rotor means operable to draw in atmospheric air for saidsecond cycle and supply the same to said lift channel means, and airinlet means in communication with said second section and disposed alongthe circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means disposed in said second section, radiallyinwardly thereof a set of spokes that rotate within said horizontalthrust channel means, and radially intermediate therebetween turbineblade means disposed within said first section,

one of said elbow section means being supplied with propulsion gases ofthe first propulsion cycle and with air of the second propulsion unitcycle jacketing the hot propulsion gases of the first cycle.

.18. A two-cycle gas turbine jet propulsion unit, comprising:

a first propulsion unit cycle including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith the output of said turbine means and continuing, on the one hand,in horizontal thrust channel means forming part of said first cycle,and, on the other, in lift channel means having a first sectionoperatively connected with said channel branching means and surroundingsaid horizontal thrust channel means, a second section surrounding saidfirst section and elbow section means operatively connected with atleast one of said first and second sections and bent approximately at anangle to the longitudinal axis of the unit, and control means in saidchannel branching means and operable to selectively control the openingand closing of said thrust and lift channel means,

a second propulsion unit cycle including said lift channel means andlift compressor rotor means operable to draw in atmospheric air for saidsecond cycle and supply the same to said lift channel means, and airinlet means in communication with said second sec- 17- tion and disposedalong the circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means disposed in said second section, radiallycentrally thereof turbine blade means disposed within said first sectionand radially inwardly thereof a set of spokes that rotate within saidhorizontal thrust channel means,

the air inlet means of the second stage effectively taking placeapproximately over the entire circumference of the propulsion unit, andadjustable control means fcr controlling said last-mentioned air inletmeans,

fuel injection means provided within at least some of the air channelsections of the second propulsion unit stage for additionallyreinforcing the lift effect,

and two lateral downwardly and outwardly directed pivotally arrangedthrust nozzle means provided at the end of each respective elbow sectionmeans.

19. A two-stage gas turbine jet propulsion unit, for propelling verticaltake-off and short take-off aircrafts, comprising;

a first propulsion uni-t stage including air compressor means,combustion chamber means operatively connected with said air compressormeans, and compressor-drive turbine means operatively connected withsaid combustion chamber means,

a channel system including channel branching means operatively connectedwith the output of said turbine means and continuing, on the one hand,in horizontal thrust channel means forming part of said first stage andextending substantially in the longitudinal axis of the propulsion unitand, on the other, in lift channel means having a first sectionoperatively connected with said channel branching means and surroundingsaid horizontal thrust channel means, a second section surrounding saidfirst section and elbow section means operatively connected with saidfirst and second sections and bent approximately at right angle to saidlongitudinal axis, and control means in said channel branching means andoperable to selectively control the opening and closing of said thrustand lift channel means,

a second propulsion unit stage including said lift channel means andlift compressor rotor means operable to draw in atmospheric air for saidsecond stage and supply the same to said lift channel means, and saidsecond section effectively constituting an air channel sectionsurrounding said first channel section and being provided with air inletmeans disposed along the circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means disposed in said second section, radiallycentrally thereof turbine blade means disposed within said first sectionand radially inwardly thereof a set of spokes that rotate within saidhorizontal thrust channel means,

the air inlet means of the second stage effectively taking placeapproximately over the entire circumference of the propulsion unit, andadjustable control means for controlling said last-mentioned air inletmeans including extensible and retractable air scoop means providedwithin the lower region of the propulsion unit circumference for thecontrol of the air inlet means, and pivotal flap means arranged in theremaining portion of the propulsion unit circumference,

fuel injection means provided within at least some of the air channelsections of the second propulsion unit stage for additionallyreinforcing the lift effect,

and two lateral downwardly and outwardly directed pivotally arrangedthrust nozzle means provided at the end of each respective elbow sectionmeans.

prising:

a first propulsion unit cycle including air compressor means, combustionchamber means operatively connected withsaid air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith the output of said turbine means and continuing, on the one hand,in horizontal thrust channel means forming part of said first cycle and,on the other, in lift channel means having a first section operativelyconnected with said channel branching mean-s and surrounding saidhorizontal thrust channel means, a second section surrounding said firstsection and elbow section means operatively connected with at least oneof said first and second sections and bent at an angle to thelongitudinal axis of the unit, and control means in said channelbranching means and operable to selectively control the opening andclosing of said thrust and lift channel means,

a second propulsion unit cycle including said lift channel means andlift compressor rotor means operable to draw in atmospheric air for saidsecond cycle and supply the same to said lift channel means, and airinlet means in communication with said second section and disposed alongthe circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means disposed in said second section, radiallyinwardly thereof a set of spokes that are aerodynamically substantiallyineffectual and rotate within said horizontal thrust channel means, andradially intermediate therebetween turbine blade means disposed withinsaid first section,

one of said elbow section means which being supplied with propulsiongases of the first propulsion unit cycle and with air of the secondpropulsion unit cycle jacketing therein the hot propulsion gases of thefirst cycle,

the air inlet means of the second cycle effectively taking placeapproximately over the entire circumference of the propulsion unit, andadjustable control means for controlling said last-mentioned air inletmeans,

fuel injection means provided within at least some of the air channelsections of the second propulsion unit cycle for additionallyreinforcing the lift effect,

and after-burner means in the horizontal thrust channel means of thefirst propulsion unit stage.

21. A twoecycle gas turbine jet propulsion unit, for propelling verticaltake-off and short take-01f aircrafts, comprising:

a first propulsion unit cycle including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith the output of said turbine means and continuing, on the one hand,in horizontal thrust channel means and, on the other, in lift channelmeans, and control means in said channel branching means and operable toselectively control the opening and closing of said thrust and liftchannel means,

a second propulsion unit cycle including lift compressor rotor meansoperable to draw in atmospheric air for said second stage and supply thesame to said lift channel means, and air inlet means for said liftchannel means disposed along the circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means, raradially centrally thereof turbine blademeans and radially inwardly thereof a set of spokes that areaerodynamically substantially ineffectual and rotate within saidhorizontal thrust channel means,

said lift channel means including elbow section means which is suppliedwith propulsion gases of the first propulsion unit cycle and with air ofthe second propulsion unit cycle,

the air inlet means of the second stage effectively taking placeapproximately over the entire circumference of the propulsion unit, andadjustable control means for controlling said last-mentioned air inletmeans.

22. A two-cycle gas turbine jet propulsion unit, for propelling verticaltake-01f and short take-off aircrafts, comprising:

a first propulsion unit cycle including air compressor means, combustionchamber means operatively connected with said air compressor means, andcompressor-drive turbine means operatively connected with saidcombustion chamber means,

a channel system including channel branching means operatively connectedwith the output of said turbine means and continuing, on the one hand,in horizontal thrust channel means extending substantially in thelongitudinal axis of the propulsion unit and, on the other, in liftchannel means having a first section operatively connected with saidchannel branching means and surrounding said horizontal thrust channelmeans substantially coaxially, a second section surrounding said firstsection and elbow section means operatively connected with said firstand second sections and bent approximately at right angle to saidlongitudinal axis, and control means in said channel branching means andoperable to selectively control the opening and closing of said thrustand lift channel means.

a second propulsion unit cycle including lift compressor rotor meansoperable to draw in atmospheric air for said second stage and supply thesame to said lift channel means, and air inlet means for said liftchannel means disposed along the circumference of the propulsion unit,

and said lift compressor rotor means carrying radially outwardly thereofair compressor blade means, radially centrally thereof turbine blademeans and radially inwardly thereof a set of spokes that areaerodynamically substantially ineffectual and rotate within saidhorizontal thrust channel means,

said lift channel means including elbow section means which is suppliedwith propulsion gases of the first propulsion unit cycle and with air ofthe second propulsion unit cycle,

the air inlet means of the second stage effectively taking placeapproximately over the entire circumference of the propulsion unit, andadjustable control means for controlling said last-mentioned air. inletmeans,

fuel injection means provided within the lift channel means forreinforcing the lift effect,

and two lateral downwardly and outwardly directed pivotally arrangedthrust nozzle means provided at the end of the elbow section means.

23. In a two-stage gas turbine jet propulsion unit, for propellingvertical take-off and short take-off aircrafts, which includes a firstpropulsion unit cycle with air compressor means, combustion chambermeans and compressor-drive turbine means; a channel system including achannel bifurcation operatively connected with the output of saidturbine means and continuing, on the one hand, in a horizontal thrustchannel and extending substantially in the longitudinal axis of thepropulsion unit and, on the other, in lift channel bent at an angle tosaid longitudinal axis, and control means in said bifurcation operableto selectively control the opening and closing of said thrust and liftchannels; and a second propulsion unit cycle including lift compressorrotor means operable to draw in atmospheric air for said second cycleand supply the same to said lift channel, and air inlet means for thesecond cycle disposed along the circumference of the propulsion unit,

the improvement essentially consisting of blade means carried by saidlift compressor rotor means including air compressor blade meansdisposed radially outwardly thereof, a set of spokes radially inwardlythereof that are aerodynamically substantially ineffectual and rotatewithin said thrust channel means, and turbine blade means intermediatesaid air compressor blade means and said spokes,

said lift channel including an initially approximately longitudinallydirected and subsequently downwardly bent lift-channel branch which issupplied with propulsion gases of the first propulsion unit cycle andwith air of the second propulsion unit cycle,

fuel injection means provided within at least some of the air channelsections of the second propulsion unit cycle,

and after-burner means in the thrust channel of the first propulsionunit cycle.

References Cited by the Examiner UNITED STATES PATENTS FOREIGN PATENTS12/1961 Ger-many.

MARK NEWMAN, Primary Examiner.

16. IN A TWO-STAGE GAS TURBINE JET PORPULSION UNIT, FOR PROPELLINGVERTICAL TAKE-OFF AND SHORT TAKE-OFF AIRCRAFTS, WHICH INCLUDES A FIRSTPORPULSION UNIT CYCLE WITH AIR COMPRESSOR MEANS, COMBUSTIOIN CHAMBERMEANS AND COMPRESSOR-DRIVE TURBINE MEANS; A CHANNEL SYSTEM INCLUDING ACHANNEL BIFURCATION OPERATIVELY CONNECTED WITH THE OUTPUT OF SAIDTURBINE MEANS AND CONTINUING, ON THE ONE HAND, IN A HORIZONTAL THRUSTCHANNEL AND EXTENDING SUBSTANTIALLY IN THE LONGITUDINAL AXIS OF THEPROPULSION UNIT AND, ON THE OTHER, IN LIFT CHANNEL BENT AT AN ANGLE TOSAID LONGITUDINAL AXIS, AND CONTROL MEANS IN SAID BIFURCATION OPERABLETO SELECTIVELY CONTROL THE OPENING AND CLOSING OF SAID THRUST AND LIFTCHANNELS; AND A SECOND PROPULSION UNIT CYCLE INCLUDING LIFT COMPRESSORROTOR MEANS OPERABLE TO DRAW IN ATMOSPHERIC AIR FOR SAID SECOND CYCLEAND SUPPLY THE SAME TO SAID LIFT CHANNEL, AND AIR INLET MEANS FOR THESECOND CYCLE DISPOSED ALONG THE CIRCUMFERENCE OF THE PROPULSION UNIT,THE IMPROVEMENT ESSENTIALLY CONSISTING OF BLADE MEANS CARRIED BY SAIDLIFT COMPRESSORE ROTOR MEANS INCLUDING AIR COMPRESSOR BLADE MEANSDISPOSED RADIALLY OUTWARDLY THEREOF, A SET OF SPOKES RADIALLY INWARDLYTHEREOF THAT ARE AERODYNAMICALLY INEFFECTUAL AND ROTATE WITHIN SAIDTHRUST CHANNEL MEANS, AND TURBINE BLADE MEANS INTERMEDIATE SAID AIRCOMPRESSOR BLADE MEANS AND SAID SPOKES. SAID LIFT CHANNEL INCLUDING ANINITIALLY APPROXIMATELY LONGITUDINALLY DIRECTED AND SUBSEQUENTLYDOWNWARDLY BENT LIFT-CHANNEL BRANCH WHICH IS SUPPLIED WITH PROPULSIONGASES OF THE FIRST PROPULSION UNIT CYCLE AND WITH AIR OF THE SECONDPROPULSION UNIT CYCLE.